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Nonlinear aeroservoelastic modelling and analysis of aircraft with control surface freeplay
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thesis_UY_v01_2022_12_22.pdf
Date
2022-11-24
Author
Yurtsever, Utku
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In this study, nonlinear aeroservoelastic analysis of aircraft with control surface freeplay is performed using the fictitious mass approach. For the demonstration of the nonlinear aeroservoelastic analysis methodology, an available very light aircraft (VLA) design configuration is selected. The aeroelastic model of the aircraft is obtained by combining the structural and aerodynamic models of the aircraft, which are prepared by the finite element modelling and analysis tool MSC.Patran/MSC.Nastran and the aeroelastic solver ZAERO, respectively. Nonlinear aeroservoelastic model of the aircraft is obtained by integrating the control surface freeplay models and the flight control algorithm created using MATLAB. The nonlinear effects of different control surface freeplays on the aircraft are investigated at various flight conditions. The results with aileron, elevator, and rudder freeplays show that for the particular aircraft studied, elevator is the most critical control surface in terms of nonlinear aeroservoelastic behavior of the aircraft leading to instability, and the freeplay in the rudder has no effect on the instability of the aircraft.
Subject Keywords
Aeroelasticity
,
Aeroservoelasticity
,
Nonlinear aeroservoelastic modelling
,
Freeplay
,
Fictitious mass approach
URI
https://hdl.handle.net/11511/101193
Collections
Graduate School of Natural and Applied Sciences, Thesis
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U. Yurtsever, “Nonlinear aeroservoelastic modelling and analysis of aircraft with control surface freeplay,” M.S. - Master of Science, Middle East Technical University, 2022.